JPH04158198A - Steering blade locking device for missile - Google Patents

Abstract

PURPOSE:To improve reliability and to eliminate remainder of a locking device in a missile having a rocket motor by providing a steering blade restricting member engaged with a steering blade and an energizing unit for pressing the member to a body wall to be collapsed by thrust force or discharge heat of the motor at the time of launching. CONSTITUTION:Before a missile is launched, a restricting member 1 is pressed fixedly to the outer periphery of an airframe 5 by a spring 2. Accordingly, the slit 1a of the member 1 is engaged with a steering blade 3 to prevent rotation of the blade 3 around a hinge 6a. When the missile is launched, a rocket motor 4 is ignited, and the spring 2 is collapsed by generated thrust force or discharge heat. The restricting force of the member 1 is lost, it is separated from the airframe 5 upon sliding on the outer periphery of the airframe by the inertial force or the thrust force of the motor 4 at the time of launching, the locking state of the blade 3 is released, and the blade 3 can be steered by a servo actuator 6. It has a low cost and high reliability. The weight of the missile can be reduced by separating it from the airframe at the time of launching.

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention has a method of restraining the rotation of the steering blade of a flying object before launch and holding it in a predetermined position, and releasing the restraint of the steering blade at the time of launch. This invention relates to a locking device for a control wing of a flying vehicle.

[Conventional technology]

Most flight gymnastics steering systems include a device that restrains unnecessary free rotation of the steering wing due to swinging of the aircraft body or the like when inactive before launch.

FIG. 2 shows a conceptual diagram of a conventional steering wing locking device for a flying vehicle.

Conventional locking mechanisms utilize a locking pin or brake mechanism 22 driven by a linear actuator 21 mounted inside the fuselage 5 and powered by hydraulic, pneumatic, electromagnetic, etc. forces.

That is, in the locked state, the lock pin or brake mechanism 22 engages with the recess of the steering blade 24 and
The drive power transmission path 2 is mechanically restrained at a steering angle of 0°, and when releasing the lock when launching the flying object, the drive power transmission path 2
By supplying hydraulic or pneumatic pressure or electric power from a power source for the steering system to the linear actuator 21 through the linear actuator 3, the lock pin or brake mechanism 22 is driven and unlocked.

Note that 25 in FIG. 2 is the hinge line of the steering blade.

[Problem to be solved by the invention]

The above-mentioned conventional steering wing locking device for a flying body includes (a)
There are many parts.

(b) The power for driving the lock device is supplied from the steering device power source.

(C) A transmission path for power and control signals is required.

(d) A locking mechanism is installed inside the aircraft.

Therefore, there are the following problems.

(1) Low reliability.

(2) It occupies a large space.

(3) It is heavy.

(4) Power consumption is large.

(5) The conch device remains in the body even after it is released.

The present invention aims to provide a steering wing locking device for an aircraft that can solve the above problems.

[Means to solve the problem]

The steering vane locking device for a flying body of the present invention is used in a flying body equipped with a steering vane attached to the outside of the fuselage and a rocket motor that generates propulsive force, so as to engage the steering vane and come into contact with the fuselage wall. The aircraft is equipped with a restraining member for the steering wing located at the rear of the aircraft, and a biasing device that presses the restraining member against the fuselage wall and is ruptured by the thrust of the rocket motor or exhaust heat during launch.

[Effect]

In the present invention, before the flying object is launched, the restraining member is pressed against the fuselage wall by the urging device and fixed to the fuselage by frictional force. Therefore, the restraining member engages with the steering vane to lock the steering vane and restrain its movements such as unnecessary rotation.

When a projectile is launched, the thrust of the rocket motor or exhaust heat causes the energizing device to break. As a result, the restraint member is no longer pressed against the fuselage wall, and the restraint member is separated from the fuselage by the propulsive force of the rocket motor or the inertial force during launch, and the locked state of the steering wall is released.

〔Example〕

An embodiment of the present invention will be described with reference to FIG.

Four steering blades 3, which are provided radially at an angle of 90 degrees to each other at the rear of the fuselage 5, are connected to a steering servo actuator 6 mounted inside the fuselage 5 by a hinge 6a, and It is rotated and controlled with one axis of freedom. Further, a rocket motor 4 having a rearward jetting portion 4a is provided at the center inside the fuselage 5 to generate propulsive force. Each of the steering blades 3 is inserted into the slit la of the restraint member 1 having a slit la in the axial direction that sandwiches the steering blade 3 from behind, and each of the restraint members 1 is engaged with each of the steering blades 1. The restraint member 1 is arranged so as to be able to slide around the outer periphery of the fuselage 5, and has a rear end extending inward in contact with the rear end surface of the fuselage 5, and further has a portion 1b extending forward within the ejection part 4a of the rocket motor 4. It has a U-shaped cross section. Members 1 of the restraint members 1.1 of the steering blades 3 facing each other and extending radially in opposite directions with respect to the fuselage 5
A tension spring 2 is provided that directly connects b and lb, and the spring force of the spring 2 presses the restraint member 1 to the outer periphery of the fuselage 5, and the restraint member 1 is fixed by the frictional force between them. The springs 2 are thus tensioned between the two opposing restraint members 1.1, and the two springs 2 are arranged in a cross shape as shown in FIG. 1(b). Further, the spring 2 is configured to break due to the thrust of the rocket motor 4 or exhaust heat.

In this embodiment configured as described above, during transportation or before launch when the projectile is on the launch station,
The restraining member 1 is pressed against the outer periphery of the body 5 by the spring force of the spring 2, and is fixed in that position by the frictional force. Therefore, the slit la of the restraining member 1 engages with the steering blade 3,
Rotation of the steering blade 3 around the hinge 6a is prevented.

When launching a projectile, the rocket motor 4 is ignited by a launch command signal. The spring 2 is broken by the thrust or exhaust heat generated at this time. by this,
The restraining force of the restraining member 1 is lost, and the restraining member 1 slides around the outer circumference of the aircraft and is separated from the aircraft 5 by the inertia force during launch or the propulsive force of the rocket motor 4, and the steering wing 3 is in the locked state. is released, and the steering blade 3 can thereafter be steered by the servo actuator 6.

As described above, in this embodiment, before the projectile is launched, rotation of the steering blade 3 around the hinge 6a is reliably prevented, and at the time of launch, the thrust of the location motor or the exhaust The wings 2 are broken by the heat, the restraint member 3 is separated from the fuselage 5, and the locked state of the steering blade 3 is released.

Therefore, no power is required to drive the locking device, and
It can occupy less space and weight. Furthermore, the restraining member 3 and the wings 2 do not remain inside the projectile, and the weight of the projectile can be reduced.

In this example, the positioning of each restraining member 1 is as follows:
This is done by fitting the restraining member 1 into a groove provided on the rear end surface of the fuselage 5 in the same phase as the steering blade 3.

In this embodiment, the restraint member 1 is pressed against the fuselage wall using the springs 2, but instead of the springs, a biasing device such as a wire that connects and pulls the opposing portions lb of the restraint member 1 is used. , the restraining member 1 may be pressed against the body wall by an urging force such as a tensile force.

〔Effect of the invention〕

As explained above, in the present invention, the following features are required in conventional devices: (1) sharing of the power source for driving the lock mechanism and the power source for the steering device; (2) transmission path for power and control signals; and (3) lock device. This eliminates the need for space inside the fuselage, making it possible to reliably lock the control blades and prevent their movement before launch.In addition, during launch, the locking device can be reliably separated from the fuselage without requiring power, allowing the control blades to be locked securely and prevented from moving. can be unlocked. Therefore, the steering wing locking device according to the present invention is inexpensive, highly reliable, lightweight, does not require space inside the aircraft body, saves energy, and can be separated from the aircraft body at the time of launch. Effects such as weight reduction can be achieved.

[Brief explanation of drawings]

FIG. 1(a) is a sectional view of one embodiment of the present invention, FIG. 1(b)
) is a sectional view taken along arrow A in FIG. 1(a) showing the upper half of the same embodiment, and FIGS. 2(a) and 2) show the locking state and locking of a conventional steering blade locking device for a spacecraft, respectively. It is an explanatory view showing a release state. DESCRIPTION OF SYMBOLS 1... Restraint member, 1a... Slit of restraint member, 2... Wings, 3... Steering wing, 4... Rocket motor, 5... Airframe, 6...
・Servo actuator. Agent: Patent attorney Akira Sakama and two others (Fig. 1)

Claims (1)

[Claims] In a flying vehicle equipped with a steering wing mounted on the outside of the fuselage and a rocket motor that generates propulsion, a restraining member for the steering vane arranged to engage the steering vane and contact the fuselage wall, and the same restraint. A steering wing locking device for a flying object, characterized in that it is equipped with a biasing device whose member is crimped to the fuselage wall and is broken by the thrust of a rocket motor or exhaust heat during launch.